CN106232473A - Aircraft - Google Patents

Aircraft Download PDF

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Publication number
CN106232473A
CN106232473A CN201580020414.3A CN201580020414A CN106232473A CN 106232473 A CN106232473 A CN 106232473A CN 201580020414 A CN201580020414 A CN 201580020414A CN 106232473 A CN106232473 A CN 106232473A
Authority
CN
China
Prior art keywords
aircraft
wing
propeller unit
fuselage
flight
Prior art date
Application number
CN201580020414.3A
Other languages
Chinese (zh)
Inventor
M·舒瓦格
Original Assignee
Iat21创新航空技术有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority to ATA50121/2014A priority Critical patent/AT515456B1/en
Priority to ATA50121/2014 priority
Application filed by Iat21创新航空技术有限公司 filed Critical Iat21创新航空技术有限公司
Priority to PCT/EP2015/053294 priority patent/WO2015124556A1/en
Publication of CN106232473A publication Critical patent/CN106232473A/en

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C29/00Aircraft capable of landing or taking-off vertically
    • B64C29/0008Aircraft capable of landing or taking-off vertically having its flight directional axis horizontal when grounded
    • B64C29/0016Aircraft capable of landing or taking-off vertically having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0033Aircraft capable of landing or taking-off vertically having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C15/00Attitude, flight direction, or altitude control by jet reaction
    • B64C15/02Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
    • B64C15/12Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets the power plant being tiltable
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/02Gyroplanes
    • B64C27/021Rotor or rotor head construction
    • B64C27/026Devices for converting a fixed wing into an autorotation rotor and viceversa
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/20Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C3/00Wings
    • B64C3/38Adjustment of complete wings or parts thereof
    • B64C3/385Variable incidence wings
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C3/00Wings
    • B64C3/38Adjustment of complete wings or parts thereof
    • B64C3/56Folding or collapsing to reduce overall dimensions of aircraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C39/00Aircraft not otherwise provided for
    • B64C39/02Aircraft not otherwise provided for characterised by special use
    • B64C39/024Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02Aircraft characterised by the type or position of power plant
    • B64D27/04Aircraft characterised by the type or position of power plant of piston type
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02Aircraft characterised by the type or position of power plant
    • B64D27/24Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/02Unmanned aerial vehicles; Equipment therefor characterized by type of aircraft
    • B64C2201/027Flying platforms
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/04Unmanned aerial vehicles; Equipment therefor characterised by type of power plant
    • B64C2201/042Unmanned aerial vehicles; Equipment therefor characterised by type of power plant by electric motors; Electric power sources therefor, e.g. fuel cells, solar panels or batteries
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/04Unmanned aerial vehicles; Equipment therefor characterised by type of power plant
    • B64C2201/044Unmanned aerial vehicles; Equipment therefor characterised by type of power plant by internal combustion engines, e.g. oscillating piston or rotary piston engines
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/10Unmanned aerial vehicles; Equipment therefor characterised by the lift producing means
    • B64C2201/102Deployable wings, e.g. foldable or morphing wings
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/10Unmanned aerial vehicles; Equipment therefor characterised by the lift producing means
    • B64C2201/108Unmanned aerial vehicles; Equipment therefor characterised by the lift producing means using rotors, or propellers
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/16Unmanned aerial vehicles; Equipment therefor characterised by type of propulsion unit
    • B64C2201/162Unmanned aerial vehicles; Equipment therefor characterised by type of propulsion unit using ducted fans or propellers
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02Aircraft characterised by the type or position of power plant
    • B64D2027/026Aircraft characterised by the type or position of power plant comprising different types of power plants, e.g. combination of an electric motor and a gas-turbines
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D2211/00Arrangements of solar panels on aircraft

Abstract

The present invention relates to a kind of aircraft, it includes fuselage (1), multiple propeller unit (3) and wing (5), propeller unit pivots relative to fuselage (1), and wing can be at least in part relative to fuselage (1) and independent of propeller unit (3) pivot.

Description

Aircraft
The present invention relates to VTOL (VTOL) aircraft substituted, its can vertically take-off and landing, present hovering shape State, rotates around any spatial axis, moves the most in any direction, and with than known helicopter in flight forward The efficiency high with four-axle aircraft/Multi-axis aircraft reaches higher flight speed.Aircraft according to the present invention substantially by Aircraft fuselage forms, and multiple propeller unit on aircraft fuselage, preferably 3 to 10 propeller unit can be around It is perpendicular to the axis of the rotation axis of propeller and is pivoted independently from each other.In a further preferred embodiment, flight Device fuselage is supplemented with pivotable wing element, and wing element provides similar with plane flying device for aircraft in flight forward Flight characteristic.
Be embodied as having four propeller unit four-axle aircraft (such as, KR 101199536, EP 2497555 (D ' Haeryer Frederic)、US 2011/0299732(Jonchery Claire)、WO 2013/1445078(Callou Francois)、KR 20120065546(Joo Byung Kyu)、KR100812756(Kang Min Sung)、KR 100812755(Kang Min Sung)、CZ 26152(Klekner Ota)、CN 20132236591(Chen Jiayan)、RU 2500577 (Kuzmich Borzenko Jakov)) or there is the flight of Multi-axis aircraft more than four propeller unit Device corresponds to prior art, and the most each propeller unit is rigidly connected to aircraft respectively.The thrust of each propeller and rotation Wing moment of torsion is change, and aircraft is controlled by the change of revolution speed of propeller or pitch.Therefore, the side that aircraft can limit Formula takes off vertically and lands, and rotates around vertical axis, or pivots around axis of pitch, and flies on the direction limited OK.In this case, in flight forward, produce vertical lift via propeller, and proportional force component is by whole Aircraft is used for actual flight forward around the inclination limiting angle.This type of system has the disadvantages that, i.e. relatively small ratio The power of example can be used for flight forward and has relatively low flight forward speed associated with it and/or poor efficiency.
From the known a kind of configuration of KR 20120060590 (Jung Seul), wherein propeller unit can be relative to aircraft Vertical axis pivot 90 ° so that aircraft can move along the direction limited on the ground by means of each wheel rotated freely of frame Position.In state of flight, according to this description, generate vertical lift in known manner via propeller unit.
From the known a kind of configuration of CN 103359283 (Xian Bin), wherein aircraft is embodied as having three propeller lists Unit, described propeller unit can be additionally carried out pivoting.
From DE 202013008284 (Siegfried) known a kind of configuration with four rotors, wherein three Less rotor is arranged in relatively low degree, and a bigger rotor is disposed in the plane above relatively low degree.By In the additional flow guiding unit below less rotor, and/or via the pivoting action of less rotor, aircraft can be additionally Limit heading on controlled.
From the known a kind of four-axle aircraft configuration of ES 2326201 (Porras Vila), its four rigid arrangement of display Propeller unit and four pivotable flow guiding units below propeller unit so that the air-flow of spiral warp can be controlled court Forwards or towards rear.But, flow guiding unit is not suitable as wing.
From the known a kind of aircraft configuration of US 5,000,398 (Rashev Michael S.), wherein, use rigid arrangement Rotor unit generate vertical lift, and can use additional engine generate forward thrust.The fuselage providing aircraft is used for Accommodate bigger load (such as, aircraft), but there is not the wing on practical significance.
From the known a kind of aircraft configuration of US 5,419,514 (Ducan Tery A.), it is implemented as that there is aircraft machine Body, aircraft fuselage has four wings, wherein, each end that the ducted fan implemented pivotly is arranged in wing On.Wing is rigidly connected to aircraft fuselage.
From the known a kind of aircraft configuration of EP 2 690 012 (Fink Axel), it is implemented as there is aircraft fuselage also And there are four wings, wherein, approx the mass cg on aircraft fuselage is provided with main rotor, implements pivotly The front two ends that are arranged in wing of ducted fan (Mantelpropeller has the blower fan of cover) in each on.Wing rigidity Be connected to aircraft fuselage.
From the known a kind of aircraft configuration of EP 2 690 011 (Fink Axel), it is implemented as there is aircraft fuselage also And there are four wings, and wherein, approx the mass cg on aircraft fuselage being provided with main rotor, propeller is in flight Be arranged in rigidly on direction in the bigger wing in front portion of wing each on.Wing is rigidly coupled to aircraft fuselage.
From the known a kind of aircraft configuration of EP 2 690 010 (Fink Axel), it is implemented as there is aircraft fuselage also And there are two wings, and wherein, approx the mass cg on aircraft fuselage being provided with main rotor, wing is via dual Fuselage connect, thrust propeller be arranged in rigidly in the rear portion wing of wing each on.Wing is rigidly connected to flight Device fuselage.
From the known a kind of aircraft configuration of EP 2 666 718 (Eglin Paul), it is implemented as there is flight forebody also And there are four wings, wherein, approx the mass cg on aircraft fuselage is provided with the master being embodied as coaxial rotor Rotor, propeller is arranged on the bigger wing in front portion of wing on heading rigidly.Wing is rigidly connected to flight Device fuselage.
From the known a kind of aircraft configuration of RU 2502641 (Durov Dmitrij Sergeevich), it is by being arranged in parallel Two aircraft fuselages constitute and there are two wings, wherein three rotors are arranged on aircraft fuselage, ducted fan It is arranged in rigidly on the rear portion wing of wing and generates forward thrust.Wing is rigidly connected to aircraft fuselage.
The known a kind of aircraft configuration of KR 20130126756 (Kroo Ilan), is implemented as having aircraft fuselage also And there are four wings, wherein, the vertical spin oar of multiple arranged in series is transversely disposed on aircraft fuselage, and propeller is firm Be arranged in two, the rear portion wing of wing to property each on.Wing is rigidly connected to aircraft fuselage.
From the known a kind of all-wing aircraft design of CN 103318410 (Wang Jin), it is implemented as that there are two pivotable spirals Oar and can perform to take off vertically and land and also advance forward.
From the known a kind of Flight Vehicle Design of US 20130327879 (Scott Mark W.), it is implemented as that there is main rotor With the helicopter of tail rotor, tail rotor can pivot around its rotary shaft.Pivotable tail rotor stabilized flight device floating state, and And can additionally generate horizontal thrust on heading.
From the known a kind of Flight Vehicle Design of RU 2500578 (Nikolaevich Pavlov Sergej), it is implemented as tool There is aircraft fuselage, there are two propeller unit, and there are two pivotable wings in Background Region, wherein, closely As mass centre on aircraft fuselage is provided with main rotor, propeller unit is laterally arranged about aircraft fuselage In front area and parallel with heading, for forward thrust.
Arranging from WO 2003/029075 (Milde Karl F.Jr.) known multiple aircraft, wherein rigid wing is arranged On aircraft fuselage, and multiple ducted fan is connected respectively to wing or is integrated into wing, and these fan conduits add Be embodied as that there is flow guiding unit.
From the known a kind of aircraft of DE 1481620 (Lariviere Jan Soulez), two of which rigid wing is arranged On aircraft fuselage, on each end that pivotable ducted fan is arranged in aircraft fuselage, described ducted fan Realization is taken off vertically and lands also flight forward, but can not realize the smooth transition from floating state to flight forward.
From the known a kind of aircraft of US 8,016,226 (Wood Victor A.), it is by having integrated rigid wing Aircraft fuselage forms, and wherein, four pivotally-mounted ducted fans are integrated in wing, and provide aileron and lifting Rudder, for stablizing in flight forward.In the configuration, rigid wing causes high flow resistance in vertically climbing.
From the known a kind of aircraft configuration of US 8,152,096 (Smith Frick A.), it is by having flying of rigid wing Row device fuselage forms, and be additionally equipped with on two additional wings on fuselage and in aircraft front part can pivot The ducted fan turned.In the configuration, rigid wing causes high flow resistance in vertically climbing and causes instability.
From the known a kind of aircraft configuration of US 6,892,980 (Kawai Hideharu), it is by aircraft fuselage and two The rigid wing structure composition of laterally-elongated, wherein, wing structure forms four turnings, and pivotable jet engine is arranged in On each in turning.In the second embodiment variant, multiple engine arrangement being downwardly oriented are in the wing root of conventional passenger plane. In the configuration, rigid wing causes high flow resistance in vertically climbing and causes instability.
From the known a kind of aircraft configuration of US 3,335,977 (Melitz Ludwig F.), wherein, two rigid wings Be arranged on aircraft fuselage, in each zone line that pivotable ducted fan is arranged in rigid wing, described in lead Manage-style fan realization is taken off vertically and lands also flight forward, but can not realize the steady mistake from floating state to flight forward Cross.
From the known a kind of aircraft configuration of US 3,360,217 (Trotter John C.), wherein, four rigid wing cloth Put on aircraft fuselage, on each end that pivotable ducted fan is arranged in rigid wing, described ducted fan Realization is taken off vertically and lands also flight forward, but can not realize the smooth transition from floating state to flight forward.Additional Jet engine be integrated in the wing of rear portion for flight forward.
The known a kind of aircraft of AT 503689 (Naderhirn Michael), it is made up of rigidity all-wing aircraft fuselage, rigidity All-wing aircraft fuselage has three the pivotable electromotors being integrated in wing.
From the known a kind of aircraft configuration of US 3,084,888 (Hertel H.), wherein, two rigid wings and multiple Motivation is arranged on aircraft fuselage, and described rigid wing and electromotor are pivotably and realization is taken off vertically and land the most oriented Front flight.
From the known a kind of aircraft configuration of DE 1926568 (Nachod James Henning), wherein, two rigidity machines The wing is arranged on aircraft fuselage, and pivotable propeller is positioned on the end of aircraft fuselage, and for forward thrust Engine arrangement is in the tail region of aircraft so that the also flight forward that takes off vertically and land is possible, but can not Flight forward smoothly it is transitioned into from floating state.
The known a kind of aircraft configuration of US 20130256465 (Smith Dudley E.), wherein, two rigid wing cloth Putting on aircraft fuselage, pivotable rotor is arranged on the end of aircraft fuselage, described rotor realize take off vertically and Land and also have flight forward, but the smooth transition from floating state to flight forward can not be realized.
From the known a kind of aircraft configuration of WO 2005/037644 (Dzerins Peteris), being implemented as having can pivot Turn the Multi-axis aircraft of the propeller arranged so that the also flight forward that takes off vertically and land is possible, but can not glide , because there is not wing element in flight.
From the known a kind of aircraft configuration of DE 102011113731 (Euer Hartmut), wherein, two rigid wing cloth Putting on aircraft fuselage, rigid wing supports pivotable electromotor, and further, pivotable electromotor is at rear portion Region is arranged on aircraft fuselage so that the also flight forward that takes off vertically and land is achieved, and also realize from Floating state is to the smooth transition of flight forward.
From the known a kind of aircraft configuration of EP 2 669 195 (Euer Hartmut), wherein, multiple driving rotors are arranged On pivotal arm on aircraft fuselage, drive rotor to realize taking off vertically and landing also flight forward, and drive rotor It is pressed against fuselage or wing in the second position, or is contained in fuselage or wing, and described aircraft is implemented into and had Vertical and lateral tail units is for stablizing in mission phase.In another embodiment variant, wing can around transverse to The axis of the longitudinal axis of aircraft is pivoted.
All known aircraft configuration are respectively provided with following shortcoming: lack efficiency in flight forward, and/or lack Around complete 360 ° of navigabilities of every radical space axis, and/or lack stablizing from floating state to flight forward Cross.
The purpose of the present invention is for limiting a kind of aircraft, and this aircraft can take off vertically and land, and presents floating state, encloses Rotate around every radical space axis, move the most in any direction, and with than known helicopter and four in flight forward The efficiency that axle aircraft/Multi-axis aircraft is high realizes higher flight speed.This aircraft is during taking off and in the landing phase Between will be the compactest.In the case of propeller unit breaks down due to unit failure or shortage fuel, this flight Device will can realize safe landing by automatic rotatory power.
According to the present invention, this purpose so reaches, i.e. wing can at least in part relative to aircraft fuselage and solely Stand on each propeller unit to pivot.
Owing to multiple propeller unit are arranged such that they can pivot relative to the aircraft fuselage of rigidity and independent The thrust vectoring that ground generates can be gone up directed in any direction, and the direction of thrust vectoring is approximately parallel in flight forward Heading aligns.On fuselage the most additional wing is set in the case of, flight forward generates required lift, and phase Higher efficiency is reached in flight forward for known helicopter and four-axle aircraft/Multi-axis aircraft.Further preferably Embodiment variant in, each wing can pivot around rotary shaft so that in vertically climb (taking off vertically) and/or land behaviour Vertical period can reach higher efficiency and precision.
The number of propeller unit is 3 to 10, thus, just real with in the flight attitude higher than critical flight speed The aircraft of replacement that show stability, that only have two propeller unit is compared so that taking off vertically and the vertical landing phase Between, in floating state, and from floating state to forward advance or from the transition range proceeding forward to floating state, Stabilized flight attitude is the most all possible.
Additionally, use greater number of propeller unit, can preferably tolerate the fault of single propeller.
Propeller unit is preferably provided in wing.Propeller unit layout in wing realizes the sky to aircraft The specific aim impact of aerodynamics.
The layout of each propeller unit alternatively provided in overall aircraft structure or in wing respectively realize with The appropriateness collision of barrier, and without damage aircraft risk (such as, contact dike, be docked in vertical wall, fly over building Between little opening, such as window ...).
Propeller unit being arranged in protect-ing frame structure adds aircraft under the appropriate collision situation of barrier Safety, and achieve and can contact aircraft in operation, and without the risk that personnel are damaged.
In preferred embodiment modification, propeller unit can be arranged so that they can pivot relative to aircraft fuselage One pivoting angle, this pivoting angle is for the most about 90 ° from centre position.Therefore, except taking off vertically and landing And beyond in flight forward, thrust reversing is possible, on the one hand this significantly improve agility, the most real Show and be drawn onto on fixing underlying surfaces.
Propeller unit can pivot around pivot axis relative to aircraft fuselage, and pivot axis is parallel to the horizontal stroke of aircraft Arrange to axis, and this is applicable to each single propeller unit independently so that the most extreme flight control and having Turning to of minimum turning radius is achieved.
Can so reach the agility of aircraft and the auxiliary of navigability, i.e. propeller unit is relative to aircraft Fuselage is installed universally.
The increase of fail safe or the reduction of aircraft complexity are achieved in, i.e. propeller unit is electrically driven also And can individually be controlled.
The electric power transmission that simplifies being realized to single propeller unit by power supply is possible.Due to current typical electricity The limited capacitance of accumulator (battery) and high weight, so providing AC-battery power source in further embodiment modification, mixing electricity Source is made up of fuel cell or internal combustion engine and electromotor for generating electric energy.
Piloted vehicle and the mileage of unmanned vehicle and use time have great importance, for This additionally provides solaode for generating electric energy.
By means of at least one oil-engine driven propeller unit, there is self-powered mileage on board the aircraft Can be favourable with the use time.
On the one hand the aircraft agility that increases and the on the other hand high efficiency in flight forward by following so Be possibly realized, i.e. wing can pivot around an axis relative to aircraft fuselage, and described axis is relative to the lateral shaft of aircraft Line is arranged in parallel or acutangulates layout, and in economic flight forward, an adjustment angle can adjust wing, described Adjust angle and realize minimum possible flow resistance with optimal lift.
By make wing be arranged to they collapsible and may be provided in extremely the narrowest space take-off and landing and Also has the least radar signature.
Higher height is arrived by following such one-tenth than using known helicopter/four-axle aircraft/Multi-axis aircraft For possible, i.e. wing is movable to spiral helicine pivot position, in this position, and/or encloses around its vertical axis at aircraft In the case of the axle being parallel to vertical axis (but in aircraft exterior) rotates, generate vertical lift, to use by the low energy Carry out climb (being similar to eagle aloft " spiral ").
The present invention will be explained in more detail based on Fig. 1 to Fig. 5 below:
Fig. 1 illustrates the aircraft according to the present invention, and it includes that aircraft fuselage 1, outer protection framework 2 (are not definitely to need Want), multiple, preferably 4 propeller unit 3, the pivoting unit 4 for each propeller unit 3, headings 6, this flight Direction 6 can be by possible around vertical axis 7, axis of pitch 8 and longitudinal axis 9 of the position of propeller unit and aircraft Rotary motion limits.
Fig. 2 illustrates the aircraft according to the present invention, its pivoting unit 4 with propeller unit 3 and pivot member 4 ', its Middle pivoting angle can be more than +/-180 °.
Fig. 3 illustrates the top view of the aircraft according to embodiments of the invention modification, and it has wing 5, and wing 5 is rigidity , or according to further embodiment modification, wing 5 can pivot a pivoting angle 5 along pivotal axis 5 ' ", wherein pivoting angle 5 " preferably in the range of +/-90 °.Aircraft is positioned on the heading 6 in advancing forward, and propeller unit 3 exists Align on heading.
Fig. 4 illustrates the side view of the aircraft according to Fig. 3 according to the present invention.Wing 5 is by adjusting angle 5 " with flight It is adjusted, for generating optimal lift in opposite directionly.
Fig. 5 illustrates the aircraft being in optimal flight forward according to the present invention, and it has the most controlled wing 5, These wings 5 are arranged on aircraft fuselage 1.Propeller unit 3 and pivoting unit 4 can be protected by protect-ing frame structure 2.Flight Device fuselage 1 and protect-ing frame structure 2 can have aerodynamic shape.
Fig. 6 illustrates the aircraft according to the present invention, and it has laterally folded wing, for the least external dimensions, As such as needed for landinging control in little space.
Fig. 7 illustrates the aircraft according to the present invention, and it has the wing adjusted in the opposite direction so that aircraft can quilt It is arranged around vertical axis to rotate, vertically moves being similar to propeller, or break down in propeller unit In the case of can be simultaneously set in downward direction rotating in 6 of free-falling in vertical direction around vertical axis, And can absorb, in mode timely, the shock that the resistant function of wing dropping is caused when utilizing rotating energy.
Fig. 8 illustrates the aircraft in further embodiment modification according to the present invention, wherein single aircraft list Unit 3 is directly arranged on wing, and this aircraft has folded wing, for the safety during take-off process or in little space Stably stand on the ground during landing.
Fig. 9 illustrates the aircraft in the further embodiment modification according to Fig. 8 according to the present invention, and wherein each is independent Propeller unit 3 be directly arranged on wing, and wing has launched after take-off process.
Figure 10 illustrates the aircraft in the further embodiment modification according to Fig. 8 according to the present invention, and wherein each is single Only propeller unit 3 is directly arranged on wing, and has launched in the flight forward that wing is after take-off process, its The behavior in this takeoff phase of the middle aircraft is similar to conventional planar aircraft (such as, the power flide with low flow resistance Machine).
The basic sides of the present invention also resides in aircraft and can be embodied as without afterbody or the surface of stability.

Claims (16)

1. an aircraft, described aircraft has aircraft fuselage (1) and multiple propeller unit (3) and has wing (5), described propeller unit is arranged so that they are pivotable relative to described aircraft fuselage (1), and described wing can be at least It is partly relative to described aircraft fuselage (1) and pivots independent of described propeller unit (3), it is characterised in that be described In propeller unit (3) is arranged on wing (5) or in described aircraft fuselage (1).
Aircraft the most according to claim 1, it is characterised in that be provided with 3 to 10 propeller unit (3).
3. according to the aircraft according to any one of claim 1 or 2, it is characterised in that described propeller unit (3) has respectively Protected framework.
Aircraft the most according to any one of claim 1 to 3, it is characterised in that described propeller unit (3) can be relatively Pivoting a pivoting angle in described aircraft fuselage (1), described pivoting angle is for start the most about from centre position It it is 90 °.
Aircraft the most according to any one of claim 1 to 4, it is characterised in that described propeller unit (3) is around one Pivot axis is pivotable relative to described aircraft fuselage (1), and described pivot axis is parallel to the axis of pitch of described aircraft Arrange.
Aircraft the most according to any one of claim 1 to 4, it is characterised in that described propeller unit (3) relative to Described aircraft fuselage (1) is installed universally.
Aircraft the most according to any one of claim 1 to 6, it is characterised in that described propeller unit (3) is that electricity drives Move, and preferably provide solaode for generating electric energy.
Aircraft the most according to claim 7, it is characterised in that providing AC-battery power source, described AC-battery power source is by fuel cell Or the internal combustion engine and electromotor for generating electric energy is constituted.
Aircraft the most according to any one of claim 1 to 6, it is characterised in that described propeller unit (3) is by extremely A few internal combustion engine drives.
Aircraft the most according to any one of claim 1 to 9, it is characterised in that described wing (5) is around an axis Pivotable relative to described aircraft fuselage (1), described axis is arranged in parallel relative to the axis of pitch of described aircraft or becomes Acute angle is arranged.
11. aircraft according to any one of claim 1 to 10, it is characterised in that described wing (5) is with folding Mode is arranged.
12. according to the aircraft according to any one of claim 1 to 11, it is characterised in that described wing (5) can move to spiral shell In the pivot position of rotation shape, in this pivot position, during described aircraft rotates, generate lift around its vertical axis.
13. according to the aircraft according to any one of claim 1 to 13, it is characterised in that occur at single driver element In the case of fault, common by described wing (5) pivots and the vertical subsidence of described aircraft so that described aircraft enters Entering rotation automatically, and impact energy on the ground relaxes in the following manner, the most described wing is contrary with the first pivot It is adjusted in mode timely on direction, and lift can be generated by described rotation.
14. according to the aircraft according to any one of claim 1 to 13, it is characterised in that propeller unit (3) energy rigidity Or movably mode is arranged on described wing (5).
15. according to the aircraft according to any one of claim 1 to 14, it is characterised in that described aircraft can be by means of institute State wing on described ground, present stable standing.
16. according to the aircraft according to any one of claim 1 to 15, it is characterised in that have the described of the wing turned up Aircraft can take off vertically, and can be launched by described wing (5) in described floating state, and wherein said aircraft is preferably Stable flight forward can be transitioned into from described floating state, and high flight speed can be presented in the case of minimum flow resistance Degree.
CN201580020414.3A 2014-02-18 2015-02-17 Aircraft CN106232473A (en)

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EP3107807A1 (en) 2016-12-28

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